|Publication number||US7318717 B2|
|Application number||US 10/315,464|
|Publication date||Jan 15, 2008|
|Filing date||Dec 10, 2002|
|Priority date||Mar 16, 2000|
|Also published as||EP1265826A1, US6521152, US7234571, US20030108635, US20030127291, US20080150183, WO2001068556A1|
|Publication number||10315464, 315464, US 7318717 B2, US 7318717B2, US-B2-7318717, US7318717 B2, US7318717B2|
|Inventors||Michael D. Wood, Mark L. LaForest, Neil Murdie, Dean S. Kriskovich, Vernon R. Hudalla, Thaddeus W. Gonsowski|
|Original Assignee||Honeywell International Inc.|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (21), Referenced by (12), Classifications (24), Legal Events (3)|
|External Links: USPTO, USPTO Assignment, Espacenet|
This is a division of U.S. patent application Ser. No. 09/527,322 filed Mar. 16, 2000, now U.S. Pat. No. 6,521,152 B1.
1. Field of the Invention
The present invention relates to a method and apparatus for forming fiber reinforced composite parts.
2. Description of the Related Art
Fiber-reinforced composite structures, such as carbon-carbon composites for example, are widely used as friction materials for heavy-duty brakes in automobiles, trucks, and aircraft. This is because they exhibit high thermal conductivity, large heat capacity, and excellent friction and wear characteristics and thus can provide excellent performance.
However, past manufacturing processes for producing these fiber-reinforced composite structures were often lengthy undertakings, requiring months to fabricate a single part. In one example, a typical fiber-reinforced composite part was prepared by a non-woven process that involved needle-punching layers of carbon fibers to form a preform, a slow, time-consuming process. When two or more layers of fibers are needle punched together by metal needles having barbs on one end, the barbs commingle fibers from a particular layer into successive layers. The commingled fibers essentially stitch the layers of fiber together. This nonwoven technology achieved preform densities on the order of about 0.5 g/cc. To obtain a final composite part, the preform was subsequently infiltrated with a matrix binder material via a chemical vapor deposition (“CVD”) or chemical vapor infiltration (“CVI”) process, for example. CVD and CVI are used interchangeably for the purposes of the present application.
In another process, a preform was prepared by building up successive layers of pre-impregnated carbon fiber fabric. Tows (the term “tow” is used hereinafter to refer to a strand of continuous filaments) of carbon fiber were woven into a two-dimensional fabric, and thereupon dipped into a liquid bath to impregnate the fabric with a liquid resin. The resin-impregnated fabric was then pulled between rollers to form a sheet of pre-impregnated carbon-fiber fabric. After impregnation, the fabric was dried and b-staged under low heat. A plurality of desired shapes were then cut out of the sheet material and stacked within a mold, and subsequently cured using heat and pressure to obtain the desired composite part. In order to produce a carbon-carbon component, the composite part is carbonized which creates internal porosity. Multiple infiltration cycles using CVD or resin were required to achieve final density of the composite part. For this reason, it often took a term of several months to obtain a final product, causing the product to be extremely expensive. Further, much material was wasted in order to obtain the final product.
Several processes have been developed in order to reduce overall processing time needed to manufacture a fiber reinforced composite part. One process, a “random-fiber process”, uses entirely tow material. Somewhat similar to the pre-impregnating method described above, in the random-fiber process a continuous tow of fiber is dipped through a resin bath, dried, and then chopped to a desired length. The resin coated chopped fibers are then placed into a mold and cured using heat and pressure. However, the steps of impregnating the continuous tow are performed separately from the molding and curing required to create the composite part, thereby extending the “process cycle” of manufacturing the composite part.
Another method involves a molding compound process whereby chopped fibrous material are mixed with a resin so as to form a continuous sheet of mixed material. A plurality of desired shapes are then cut out of the sheet material and stacked within a mold, and subsequently cured using heat and pressure to obtain the desired composite part. Again, this process requires extensive time and wastes material in order to obtain the final product.
A further process developed to shorten the manufacturing time involves using a liquid slurry to mix the fibrous material with a resin powder, as illustrated in U.S. Pat. No. 5,744,075 to Klett et al. However, the fibrous material needs to be chopped into small pieces (on the order of ¼ to ½ inch (about 0.6-1.3 cm)) so as to attain a uniform mix with the resin powder in the slurry. Thus, longer chopped fibers (1-1 ½ inches (about 2.5-3.8 cm)) do not work well in this liquid slurry method, since a uniform dispersion of fibrous material and resin powder in the slurry cannot be attained with the longer chopped fiber lengths. The longer fibers tended to “ball-up” during mixing with the powdered resin and during deposition into the mold, making it difficult to obtain a uniform end product. Moreover, this “balling effect” directly contributed to the “loftiness” of the preform, a disadvantageous result of the water slurry method since a lofty preform was difficult to control within the mold. Additionally, an excess step of drying the preform was required (i.e., removing the water from the preform in the heating step is required before pressing the materials into a composite part).
Recent developments have introduced a method and apparatus that combines chopped fibers and a powdered resin utilizing a dry-blending process. Such a dry-blending process and apparatus 100 is illustrated in the rough schematic diagram of
The broken-up fibers 118 entrained in air in the upper section 117 are then forced through neck portion 119 into a second enclosure 102, whereby they are mixed with a powdered resin 130 fed through at funnel 132 of second enclosure 102. The powder resin 130 mixes with the broken-up fibers in a powder and fiber mixing region 140, whereupon the “mixed materials” settle at the bottom of second enclosure 102 to form a layer which constitutes the building-up of a preform 125. The mixed materials fall due to a vacuum 135 being applied to the bottom of second enclosure 102 which removes the bulk of the air volume in second enclosure 102, thereby allowing the mixed materials to fall and condense at the bottom of second enclosure 102 on top of screen 126.
The “dry-blending” apparatus of
Yet a further process to shorten the manufacturing cycle time of a composite part is illustrated in U.S. Pat. No. 5,236,639 to Sakagami et al. The objective of this process is to provide excess carbon material to fill pores in the matrix material during subsequent curing and carbonization steps, thus producing a carbon-carbon composite material that requires no repetition of production steps including any further densification of the composite material. This involves mechanically mixing a matrix carbon material and carbon fibers in proportions that are determined on the basis of the carbonization ratio of the matrix material and on the basis of the desired ratio of fibers to be contained in a resultant end product. However, such a process requires the use of excess carbon matrix material, a curing step under pressure after formation of an intermediate-formed part such as a preform or mold, and also requires subsequent carbonization and graphitization of the cured intermediate part, both under pressure, to obtain the final fully-densified composite part. Of course, no further production steps are required or repeated, including densification of the composite material. However, it is costly and time consuming to perform the curing, carbonization and graphitization all under pressure.
Therefore, what is desired is a method and apparatus which would feed, blend, and deposit various lengths of chopped fibrous and binder materials into a mold of a desired final shape, wherein the raw fibrous materials and binder materials are combined in a single step, followed by consolidation of the materials. The resultant preform would not require any curing or carbonization under pressure during the follow-on heating processes to manufacture the final composite part. Such a method and apparatus would provide fiber-reinforced composite parts with densities that are higher than achieved with current technologies, and would decrease overall cycle time to a finished composite part. The method can be used to provide an intermediate preform product that is subsequently stabilized, carbonized, optionally heat treated, densified, and final heat treated to provide a carbon-carbon composite material.
The present invention provides a method and apparatus for combining raw fibrous and binding materials in a single mixing step, followed by consolidation so as to greatly shorten the overall cycle time to a finished fiber-reinforced composite part. In the method, chopped fibers, which can include single length or multiple lengths of fibrous material, and a powdered resin binder material are combined in a continuous process at predetermined ratios, mixed together, and deposited into a mold having the shape of the final product. Specifically, the chopped fibrous materials and binder materials are deposited sequentially onto a belt conveyor so that the materials are successively layered in a predetermined ratio, and subsequently mixed to achieve uniform dispersion throughout. The “mixed materials” are then deposited into a rotating mold to further ensure uniform dispersion of fibrous and binder materials, wherein impregnation of the fibrous materials with the binder material occurs in-situ as the uniformly mixed materials are heated in the mold, and subsequently compacted to obtain the final desired shape of the preform. The resultant preform requires no excess use of matrix material, no curing or carbonization under pressure in the follow-on heating processes required to obtain the intermediate fiber-reinforced composite part.
Objectives of the present invention will become more apparent from the detailed description given hereinafter. However, it should be understood that the detailed description and specific examples, while indicating preferred embodiments of the invention, are given by way of illustration only, since various changes and modifications within the spirit and scope of the invention will become apparent to those skilled in the art from this detailed description.
The present invention will become more fully understood from the detailed description given hereinbelow and the accompanying drawings, wherein like elements are represented by like reference numerals, which are given by way of illustration only, and thus are not limitative of the present invention and wherein:
The method and apparatus in accordance with the preferred embodiment enables the production of fiber-reinforced composite parts suitable for use in manufacturing various components, including materials for high-friction applications such as automobile, truck, and aircraft brakes. By combining fibrous materials with a binder material in a single apparatus, a fiber-reinforced composite part with improved friction and wear performance can be produced in fewer processing steps as compared to the current techniques of the related art used to fabricate fiber-reinforced composite materials, thereby providing increased reliability and reduced process cycle times. Additionally, the preferred embodiment allows for more complete control over defibrillation of carbon fibers so as to obtain a sufficient balance between strength/wear properties with adequate dispersion of mixed carbon fiber and matrix resin materials, as compared to other manufacturing processes such as using a liquid slurry, for example.
Feeder 210 may feed reinforcing fibers between about 0.5-1.5 inches (about 1.3-3.8 cm) in length at a first predetermined rate. Preferably, feeder 210 feeds 1-inch (2.54 cm) fibers (hereinafter “reinforcing fiber”); however, reinforcing fibers longer than 1.5 inches (3.8 cm) may be used. Feeder 220 may feed milled and short fibers between about 0.004 inch (0.1 mm) and ½ inch (1.27 cm) in length, and preferably feeds 0.004 inch (0.1 mm) length fiber (hereinafter “milled fiber”) at a second predetermined rate. The milled fiber acts as a “filler” fiber to fill in gaps between the longer reinforcing fibers. Feeder 230 can be a resin feeder which feeds a resin binder material at a third predetermined rate. Alternatively, the fibrous materials from feeders 210 and 220 can be the same size (for example, equal length fibers up to about 1.5 inches (3.8 cm) in length. It is advantageous to use a mixture of longer and shorter fibers to obtain better friction and wear properties while still maintaining adequate strength in the finished component. The longer fibers provide the strength, while the shorter fibers fill in gaps between the longer fibers and the matrix material to help increase the final density of the intermediate-formed part/preform, and/or of the final composite part.
The chopped reinforcing and milled fibrous materials can be polyacrylonitrile (PAN) based carbon fibers, preferably to be used for fabrication of carbon-carbon composite parts. However, glass fibrous material or other reinforcing fibrous material such as metal fibers and synthetic fibers, for example may be used, depending on the resultant composite part to be fabricated. The binder material can be a high-carbon yielding mesophase pitch resin matrix (i.e., in powdered form); however, phenolic resins and other thermoplastic or thermosetting resin materials in powdered form may be used as the binder material, depending on the resultant composite part to be fabricated.
The fibrous chop and resin binder fed from feeders 210, 220, and 230 are deposited onto a belt conveyor 205 as a series of continuous, stacked layers. This provides for a semi-continuous process whereby the feeders contain a sufficient amount of materials to produce many composite parts. The stacked layers travel along belt conveyor 205 to be dispensed into a material handling fan 240. Material handling fan 240 mixes the fibrous and binder materials, while partially or fully defibrillating the chopped fiber materials from feeders 210 and 220. Alternatively, the fibrous chop and resin from the feeders may be fed directly into the material handling fan without a belt conveyer.
Material handling fan 240 further provides a volume of air flow to convey the “mixed materials” via a line 245 to cyclone dust collector 260. The cyclone dust collector 260 receives the air-entrained mixed materials and separates the solid particles from the air used to convey them. Return air fan 250 takes a suction off of cyclone dust collector 260 to circulate the bulk of the air volume coming from line 245 back to the material handling fan 240 via line 255, allowing the remaining mixed materials to gently exit the bottom of the cyclone dust collector 260 into mold 270. Dust filter fan 280 removes any residual dust created by the deposition of the mixed materials into the mold 270, and deposits dust particles into dust collector 285. To further ensure uniform deposition of the mixed materials from cyclone dust collector 260 into mold 270, the mold can be arranged on a rotation device 271.
Turntable 272 and the combination of the air cylinders 277 and linear actuator 278 provide rotational and linear motion for mold 270 during the deposition process. In operation, turntable 272 is powered by electric motor 276 via the spindle 273 to rotate the mold. Simultaneously with this rotation, mold 270 may be reciprocated in a +X and −X direction for the duration of the deposition process by air cylinders 277, the cylinders essentially jogging the support 274 supporting the turntable 272. The mold 270 is aligned to the outlet of the cyclone dust collector 260 such that it can be moved up to four (4) inches to either side of the centerline of the cyclone dust collector 260 by adjusting linear actuator 278 (for example, the linear actuator “distance” can be set at positions such as −1.0″ (−2.54 cm) or +2.5″ (+6.35 cm) from the centerline of the cyclone dust collector 260). The jogging action imparted by air cylinders 277, together with the rotation imparted by turntable 272, ensures that the mixed material falling from the bottom of the cyclone dust collector 260 is uniformly dispersed in the mold 270 as the mold 270 fills to a desired level, in preparation for a subsequent consolidation step to be discussed later below.
As shown in
Once all parameters have been initialized, the operation proceeds with sequential deposition of chopped fibrous materials and resin binder material onto conveyor belt 205 (Step S2). The layers are then mixed in a mixing step by material handling fan 240 (Step S3) and conveyed in an air volume to cyclone dust collector 260. There, the mixture of chopped fibrous material and resin binder is separated from the air volume and deposited into the rotating mold 270 (Step S4). Once the mold is filled to a desired level, a drag chain conveyor (not shown in
Once a mold 270 is filled to a desired level and removed from underneath the cyclone dust collector 260, a consolidation process is performed by heating the fiber and resin mixture, and subsequently compacting the ingredients in mold 270 to obtain an intermediate fiber-reinforced composite part of a desired shape (Step S5). During compacting, the softened resin coats and impregnates the fibrous material. After the mold is cooled below the resin softening point, the intermediate composite part or preform is ejected from the mold and subjected to follow-on heating and densification treatments so as to obtain a final, fully-densified composite part (Step S6).
The use of material handling fan 240 allows control over the amount of desired defibrillation. Particularly, and unlike conventional liquid slurry processes for example, where defibrillation is complete in breaking up a fiber tow into individual filaments, material handling fan 240 allows for a wide range of defibrillation, breaking up the chopped fibrous material into smaller filament bundles ranging from hundreds of filaments to almost 10,000 filaments, thereby preserving strength while providing improved wear properties for the resultant finished composite part. The amount of defibrillation is governed by the material handling fan speed. Keeping in mind that a minimum amount of air volume and velocity is required to convey the materials (i.e. 50% maximum speed), a lower fan speed provides less defibrillation. After mixing and defibrillation, the “mixed materials” are conveyed via line 245 to a cyclone dust collector 260 (Step S17).
To further promote uniform dispersion of the mixed materials in to the mold 270, the mold is rotated during deposition by turntable 272 (Step S19). As the mold fills with the mixed materials, a dust filter fan 285 simultaneously creates a suction on mold 270 that removes any entrained dust that is present when the mixed materials fill the mold 270 (Step S20).
Several test parts were fabricated using the above method and apparatus, specifically nine (9) stator and six (6) rotor-size parts for 767 aircraft made by the BOEING Corporation. For a stator, 3.976 pounds (1807 g) of 1-inch (2.54 cm) chop length carbon fiber (grade X9755) and 1.454 pounds (661 g) of milled carbon fiber (grade 341, each grade of fibers marketed by FORTAFIL), and 7.176 pounds (3262 g) of AR mesophase pitch resin (pellets ground into powder) marketed by the MITSUBISHI Gas Chemical Corporation were dispensed onto a belt conveyer over approximately a thirteen (13) minute period (a total of 12.606 pounds or 5723 g of “mixed material” was deposited in the mold over the time period to form a preform). The material handling fan was operating at 80% of the maximum motor speed, the return air fan at 37% of maximum motor speed and dust collector fan at 60% of maximum motor speed. The mold was located at a 2.5 inch (6.35 cm) linear position from the centerline of the cyclone dust collector and was turning 6 rpm during deposition.
For this example, the stator part was built up in two equal batches, due only to the current limitation of the 1-inch chopped fiber feeder's hopper capacity. After the fibrous and binder materials were mixed and dispensed in the mold, the mold was placed into an air circulating oven and heated to a temperature of 315° C. for four hours. After heating, the preform was compacted with 30 tons of force until mechanical stops were met. The preform thickness was maintained at 1.405″ (3.569 cm) until cool, and then was removed from the mold. The density of the 5490 g weight preform was measured at 1.35 g/cc.
Therefore the method and apparatus in accordance with the preferred embodiment enables the production of fiber-reinforced composite parts suitable for use in manufacturing various high-friction components for applications such as automobile, truck, and aircraft brakes. The density of the envisioned composite parts are between 1.2 and 1.5 g/cc. By combining low-cost chopped PAN-based carbon fibers with a high carbon yielding mesophase pitch matrix resin, a carbon/carbon composite material with improved friction and wear performance can be produced in fewer processing steps as compared to current techniques used to fabricate fiber-reinforced composite materials, thereby providing increased reliability and reduced process cycle times. Such friction materials would typically have a density of at least 1.7 g/cc.
The invention being thus described, it will be obvious that the same may be varied in many ways. For example, the constituent transport arrangement below feeders 210, 220 and 230 of
Additionally, in lieu of or in addition to performing oxygen stabilization (Step 24) of the intermediate part (
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US3348886 *||Mar 4, 1966||Oct 24, 1967||Hergeth Kg Masch Apparate||Feeding devices for fiber treating machines|
|US3594877||Oct 24, 1969||Jul 27, 1971||Yuken Kogyo Co Ltd||Apparatus for manufacturing ceramic articles|
|US3621945||Nov 12, 1969||Nov 23, 1971||Carborundum Co||Disc brakes|
|US3732345||Apr 16, 1970||May 8, 1973||Dow Chemical Co||Method for the incorporation of filamentary material in a resinous matrix|
|US3917884 *||Apr 23, 1973||Nov 4, 1975||Fiber Materials||Method of making wound graphite carbon body|
|US4002225||Feb 18, 1975||Jan 11, 1977||The Carborundum Company||Resurfaced brake discs|
|US4611445||Dec 7, 1984||Sep 16, 1986||Armstrong World Industries, Inc.||Sag-resistant ceiling panel|
|US4708268 *||Dec 6, 1984||Nov 24, 1987||Willow Technology, Inc.||Method and apparatus for the accurate volumetric feeding of materials|
|US5147588||Jun 12, 1990||Sep 15, 1992||Akebono Brake Industry Co., Ltd.||Method of making carbon/carbon composite|
|US5236639||Dec 20, 1991||Aug 17, 1993||Sumitomo Electric Industries, Ltd.||Method of manufacture composite material of carbon fibers in a carbon matrix|
|US5310025||Jul 23, 1992||May 10, 1994||Allied-Signal Inc.||Aircraft brake vibration damper|
|US5540305||Nov 7, 1994||Jul 30, 1996||Dunlop Limited||Multi-disc brake|
|US5576358||Feb 3, 1995||Nov 19, 1996||Alliedsignal Inc.||Composition for use in friction materials and articles formed therefrom|
|US5634535||Mar 8, 1996||Jun 3, 1997||Dunlop Limited||Composite brake disc|
|US5744075||May 19, 1995||Apr 28, 1998||Martin Marietta Energy Systems, Inc.||Method for rapid fabrication of fiber preforms and structural composite materials|
|US5814255||May 9, 1995||Sep 29, 1998||Durapact Gesellschaft Fur Glasfaserbetontechnologie Mbh||Process and device for the continuous production of fiber-reinforced molded bodies from hydraulically setting materials|
|US5879601 *||Jul 24, 1997||Mar 9, 1999||Baker; Richard David||Method and apparatus for the manufacture of recycled fiber reinforced resin containing products|
|US5931214 *||Aug 7, 1997||Aug 3, 1999||Howmet Research Corporation||Mold heating vacuum casting furnace|
|EP0402915A2||Jun 13, 1990||Dec 19, 1990||Akebono Brake Industry Co., Ltd.||Hybrid carbon/carbon composite material|
|EP0492491A1||Dec 20, 1991||Jul 1, 1992||Sumitomo Electric Industries, Ltd.||Method of manufacturing carbon-fiber/carbon composite material|
|WO1998043809A1||Apr 2, 1998||Oct 8, 1998||Cytec Technology Corp.||Carbon-carbon parts having filamentized composite fiber substrates and methods of producing the same|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US7700014 *||Apr 13, 2006||Apr 20, 2010||Honeywell International Inc.||VPI-RTM-CVD brake disc preform densification|
|US8721954||Mar 13, 2013||May 13, 2014||Honeywell International Inc.||Techniques for pitch densification|
|US9193113||Jul 21, 2014||Nov 24, 2015||Honeywell International Inc.||Apparatus for carbon fiber processing and pitch densification|
|US9523149||Dec 26, 2013||Dec 20, 2016||Rolls-Royce Corporation||Rapid ceramic matrix composite production method|
|US9707724||Jul 1, 2008||Jul 18, 2017||The Boeing Company||Methods and apparatus associated with narrow tows fabricated from large-tow preforms|
|US9758436||Oct 27, 2016||Sep 12, 2017||Rolls-Royce Corporation||Rapid ceramic matrix composite production method|
|US20060279012 *||Apr 13, 2006||Dec 14, 2006||Honeywell International Inc.||Carbon fiber preform densification by pitch infiltration followed by resin transfer molding|
|US20070132126 *||Dec 14, 2005||Jun 14, 2007||Shao Richard L||Method for debundling and dispersing carbon fiber filaments uniformly throughout carbon composite compacts before densification|
|US20100003881 *||Jul 1, 2008||Jan 7, 2010||Tsotsis Thomas K||Methods and apparatus associated with narrow tows fabricated from large-tow preforms|
|US20100078839 *||Jun 21, 2006||Apr 1, 2010||Honeywell International Inc.||Pitch densification of carbon fiber preforms|
|US20120104641 *||Nov 2, 2010||May 3, 2012||Honeywell International Inc.||Apparatus for pitch densification|
|US20130171286 *||Sep 13, 2012||Jul 4, 2013||Hon Hai Precision Industry Co., Ltd.||Feeding system|
|U.S. Classification||425/120, 425/200, 425/117, 427/228, 425/110, 425/DIG.108, 264/86, 425/24, 425/130, 425/447|
|International Classification||B29B15/12, B29C67/00, F16D69/02, C04B35/83|
|Cooperative Classification||B29B11/16, Y10T428/30, F16D69/023, Y10S425/108, C04B2235/5272, C04B2235/526, C04B35/83|
|European Classification||F16D69/02C, B29B15/12B, C04B35/83|
|Aug 22, 2011||REMI||Maintenance fee reminder mailed|
|Jan 15, 2012||LAPS||Lapse for failure to pay maintenance fees|
|Mar 6, 2012||FP||Expired due to failure to pay maintenance fee|
Effective date: 20120115